EASA AD No : 2010-0086R1

EASA Form 110 Page 1/2 

## EASA AIRWORTHINESS DIRECTIVE

AD No.: 2010-0086R1

Date: 16 June 2010

Note: This Airworthiness Directive (AD) is issued by EASA, acting in accordance with Regulation (EC) No 216/2008 on behalf of the European Community, its Member States and of the European third countries that parti cipate in the activities of EASA under Article 66 of that Regulation. This AD is issued in accordance with EC 1702/2003, Part 21A .3B. In accordance with EC 2042/2003 Annex I, Part M.A.301, the continuing airworthiness of an aircraft shall be ensured by accomplishing any a pplicable ADs. Consequently, no person may operate an aircraft to which an AD applies, except in accordance with the requirements of that AD, unless otherwise specified b y the Agency [EC 2042/2003 Annex I, Part M.A.303] or agreed with the Authority of the State of Registry [EC 216/2008, Article 14(4) exemption]. 

### Type Approval Holder’s Name :
AIRBUS Type/Model designation(s) :
A330 and A340 aeroplanes

TCDS Number : EASA.A.004, EASA.A.015

Foreign AD : Not applicable

Revision : This AD revises EASA AD 2010-0086 dated 04 May 2010



### ATA 92 Electric and Electronic Common Installation – Hydraulic Pump Electrical Motor Connectors – Modification

Manufacturer(s): Airbus (formerly Airbus Industrie)

Applicability: Airbus A330 aeroplanes, models -201, -202, -203, -223, -243, -301, -302, - 303, -321, -322, -323, -341, -342 and -343, all manufacturer serial numbers, except those on which Airbus modifications 58773 and 45968 have been embodied in production. Airbus A340 aeroplanes, models -211, -212, -213, -311, -312, -313, all manufacturer serial numbers, except those on which Airbus modifications 58773 and 45968 have been embodied in production. Airbus A340 aeroplanes, models -541, -542, -642 and -643, all manufacturer serial numbers, except those on which Airbus modifications 58773 and 45968 have been embodied in production.
Reason: Several A330 and A340 operators have reported in service occurrences of hydraulic pump electrical motor conn ector internal arcing, resulting in:

- either false hydraulic system over heat Electronic Centralized Aircraft Monitoring (ECAM) warnings

- and / or hydraulic pump electrical motor malfunction. Investigations have shown that, due to the manufacturing tolerances of the cables and the connectors rear grommet, there is a possible path for fluid ingress, resulting in connector internal arcing and hydraulic system malfunction. In addition, as the connectors are located in areas adjacent to fuel tanks, such arcing associated with the presence of a fuel leakage could lead to an uncontrolled fire.EASA AD No : 2010-0086R1

EASA Form 110 Page 2/2 In order to protect the hydraulic pump electrical motor connectors against fluid ingress from the rear of t he connector grommet and prevent false hydraulic system overheat ECAM warnings and/or hydraulic pump electrical motor malfunction, this AD requires modification of the three hydraulic pump electrical motor conn ectors associated to the Blue, Yellow and Green hydraulic systems.
This Revision 1 is issued to delete Airbus modifications 55923S18878 and 55924S19452 from the applicability of this AD.

Effective Date: Revision 1: 17 June 2010 Original Issue: 18 May 2010
Required action(s) and Compliance Time(s): Required as indicated, unless already accomplished : Within 3 600 flight hours after 18 May 2010 [effective date of this AD at original issue], modify the hydraulic pump electrical motor connectors of the Blue, Yellow and Green Electric Pumps in accordance with the instructions defined in Airbus Service Bulletin (SB) A330-92-3088, or Airbus SB A340-92-4081, or Airbus SB A340-92-5053, as applicable to the aeroplane model.

Ref. Publications: Airbus Service Bulle tin A330-92-3088 at Original issue, Airbus Service Bulletin A340-92-4081 at Original issue, Airbus Service Bulletin A340-92-5053 at Original issue. The use of later approved revisions of these documents is acceptable for compliance with the requirements of this AD.

Remarks: 1. If requested and appropriately substantiated, EASA can approve Alternative Methods of Compliance for this AD. 2. The original issue of this AD was posted on 19 February 2010 as PAD 10-019 for consultation until 19 March 2010. The Comment Response Document can be found at http://ad.easa.europa.eu/

. 3. Enquiries regarding this AD should be referred to the Airworthiness Directives, Safety Management & Re search Section, Certification Directorate, EASA. E-mail: ADs@easa.europa.eu

. 4. For any question concerning the te chnical content of the requirements in this AD, please contact: AIRBUS SAS – Airworthiness Office - EAL. Fax: +33 5 61 93 45 80. E-mail: airworthiness.A330-A340@airbus.com

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